Turbine vane cooling arrangement

ABSTRACT

A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

BACKGROUND

This disclosure relates to a gas turbine engine, and more particularlyto a turbine vane that may be incorporated into a gas turbine engine.The vane's airfoils and platforms include a plurality of film coolingholes as part of a cooling arrangement.

Gas turbine engines typically include a compressor section, a combustorsection and a turbine section. During operation, air is pressurized inthe compressor section and is mixed with fuel and burned in thecombustor section to generate hot combustion gases. The hot combustiongases are communicated through the turbine section, which extractsenergy from the hot combustion gases to power the compressor section andother gas turbine engine loads.

Both the compressor and turbine sections may include alternating seriesof rotating blades and stationary vanes that extend into the core flowpath of the gas turbine engine. For example, in the turbine section,turbine blades rotate and extract energy from the hot combustion gasesthat are communicated along the core flow path of the gas turbineengine. The turbine vanes, which generally do not rotate, guide theairflow and prepare it for the next set of blades.

Each of the blades and vanes include airfoils that extend into the coreflow path of the gas turbine engine between inner and outer platforms.Cooling airflow is communicated into an internal core of the airfoil andcan be discharged through the plurality of film cooling holes to providea boundary layer of film cooling air along the external surface of theairfoil and platforms. The film cooling air provides a barrier thatprotects the underlying substrate of the vane from the hot combustiongases that are communicated within the core flow path. By way of exampleU.S. Published Patent Application No. 2015/0211376 describes a holeconfiguration for a turbine vane.

SUMMARY

In one exemplary embodiment a vane includes a pair of airfoils having aplurality of film cooling holes that extend through an exterior surfaceof the airfoils, wherein each of the plurality of film cooling holesbreak through the exterior surface at geometric coordinates inaccordance with Cartesian coordinate values of X, Y and Z as set forthin Table 1, wherein each of the geometric coordinates is measured from areference point on a leading edge rail of a platform of the vane.

In another example of the above described vane the Cartesian coordinatevalues of Table 1 are expressed in inches.

In another example of any of the above described vanes the referencepoint includes a pin hole of the platform.

In another example of any of the above described vanes the plurality offilm cooling holes are spaced along a span of the airfoil body inmultiple collinearly aligned rows.

In another example of any of the above described vanes the plurality offilm cooling holes are disposed on a pressure side, a suction side and aleading edge of the airfoil body.

In another example of any of the above described vanes a first portionof the plurality of film cooling holes from a point of the airfoil bodytoward an outer platform are angled toward the outer platform and asecond portion of the plurality of film cooling holes from the pointtoward an inner platform are angled inwardly toward the inner platform.

In another example of any of the above described vanes the airfoilsextend between inner and outer platforms, the inner and outer platformsinclude another plurality of film cooling holes that extend through anexterior surface of the platforms, wherein each of the other pluralityof film cooling holes break through the exterior surface at geometriccoordinates in accordance with Cartesian coordinate values of X, Y and Zas set forth in Table 2, wherein each of the geometric coordinates ismeasured from the reference point.

In one exemplary embodiment a vane includes a pair of airfoils extendingbetween inner and outer platforms, the inner and outer platforms includea plurality of film cooling holes that extend through an exteriorsurface of the platforms, wherein each of the plurality of film coolingholes break through the exterior surface at geometric coordinates inaccordance with Cartesian coordinate values of X, Y and Z as set forthin Table 2, wherein each of the geometric coordinates is measured from areference point on a leading edge rail of a platform of the vane.

In another example of the above described vane the Cartesian coordinatevalues of Table 2 are expressed in inches.

In another example of any of the above described vanes the referencepoint includes a pin hole of the platform.

In one exemplary embodiment a vane includes a pair of airfoils extendingbetween inner and outer platforms, the inner and outer platforms includea plurality of film cooling holes that extend through an exteriorsurface of the platforms, wherein each of the plurality of film coolingholes break through the exterior surface at geometric coordinates inaccordance with Cartesian coordinate values of X, Y and Z as set forthin Table 2, wherein each of the geometric coordinates is measured from areference point on a leading edge rail of a platform of the vane.

In another example of the above described vane the Cartesian coordinatevalues of Table 2 are expressed in inches.

In another example of any of the above described vanes the referencepoint includes a pin hole of the platform.

BRIEF DESCRIPTION OF THE DRAWINGS

The disclosure can be further understood by reference to the followingdetailed description when considered in connection with the accompanyingdrawings wherein:

FIG. 1 schematically illustrates a cross-sectional view of a gas turbineengine.

FIG. 2 schematically illustrates a doublet stator vane for incorporationin a gas turbine engine.

FIG. 3 schematically illustrates a second view of the vane of FIG. 2.

FIG. 4 schematically illustrates a cross-sectional view of an airfoilhaving multiple film cooling holes as part of an airfoil coolingarrangement.

FIGS. 5A and 5B respectively illustrate outer and inner platforms of thevane including a plurality of film cooling holes as part of a platformcooling arrangement of the vane.

The embodiments, examples and alternatives of the preceding paragraphs,the claims, or the following description and drawings, including any oftheir various aspects or respective individual features, may be takenindependently or in any combination. Features described in connectionwith one embodiment are applicable to all embodiments, unless suchfeatures are incompatible.

DETAILED DESCRIPTION

FIG. 1 schematically illustrates a gas turbine engine 20. The exemplarygas turbine engine 20 is a two-spool turbofan engine that generallyincorporates a fan section 22, a compressor section 24, a combustorsection 26 and a turbine section 28. Alternative engines might includean augmenter section (not shown) among other systems for features. Thefan section 22 drives air along a bypass flow path B, while thecompressor section 24 drives air along a core flow path C forcompression and communication into the combustor section 26. The hotcombustion gases generated in the combustor section 26 are expandedthrough the turbine section 28. Although depicted as a turbofan gasturbine engine in the disclosed non-limiting embodiment, it should beunderstood that the concepts described herein are not limited toturbofan engines and these teachings could extend to other types ofengines, including but not limited to, three-spool engine architectures.

The gas turbine engine 20 generally includes a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centerlinelongitudinal axis A. The low speed spool 30 and the high speed spool 32may be mounted relative to an engine static structure 33 via severalbearing systems 31. It should be understood that additional bearingsystems 31 may alternatively or additionally be provided.

The low speed spool 30 generally includes an inner shaft 34 thatinterconnects a fan 36, a low pressure compressor 38 and a low pressureturbine 39. The high speed spool 32 includes an outer shaft 35 thatinterconnects a high pressure compressor 37 and a high pressure turbine40. In this embodiment, the inner shaft 34 and the outer shaft 35 aresupported at various axial locations by bearing systems 31 positionedwithin the engine static structure 33.

A combustor 42 is arranged between the high pressure compressor 37 andthe high pressure turbine 40. A mid-turbine frame 44 may be arrangedgenerally between the high pressure turbine 40 and the low pressureturbine 39. The mid-turbine frame 44 supports one or more bearingsystems 31 of the turbine section 28. The mid-turbine frame 44 mayinclude one or more airfoils 46 that may be positioned within the coreflow path C.

The inner shaft 34 and the outer shaft 35 are concentric and rotate viathe bearing systems 31 about the engine centerline longitudinal axis A,which is co-linear with their longitudinal axes. The core airflow iscompressed by the low pressure compressor 38 and the high pressurecompressor 37, is mixed with fuel and burned in the combustor 42, and isthen expanded over the high pressure turbine 40 and the low pressureturbine 39. The high pressure turbine 40 and the low pressure turbine 39rotationally drive the respective high speed spool 32 and the low speedspool 30 in response to the expansion.

In some non-limiting examples, the gas turbine engine 20 is ahigh-bypass geared aircraft engine. In a further example, the gasturbine engine 20 bypass ratio is greater than about six (6:1). Theexample gas turbine engine 20 can be a geared turbofan engine thatincludes an epicyclic gear train, such as a planetary gear system orother gear system. The example epicyclic gear train has a gear reductionratio of greater than about 2.3, and in another example is greater thanabout 2.5:1. The geared turbofan enables operation of the low speedspool 30 at higher speeds which can increase the operational efficiencyof the low pressure compressor 38 and low pressure turbine 39 and renderincreased pressure in a fewer number of stages.

The low pressure turbine 39 pressure ratio is pressure measured prior tothe inlet of the low pressure turbine 39 as related to the pressure atthe outlet of the low pressure turbine 39 prior to an exhaust nozzle ofthe gas turbine engine 20. In one non-limiting embodiment, the bypassratio of the gas turbine engine 20 is greater than about ten (10:1), thefan diameter is significantly larger than that of the low pressurecompressor 38, and the low pressure turbine 39 has a pressure ratio thatis greater than about 5 (5:1). It should be understood, however, thatthe above parameters are only exemplary of one embodiment of a gearedarchitecture engine and that the present disclosure is applicable toother gas turbine engines including direct drive turbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet (10,668 meters). The flight condition of 0.8 Mach and35,000 ft (10,668 meters), with the engine at its best fuelconsumption—also known as “bucket cruise Thrust Specific FuelConsumption (‘TSFC’)”—is the industry standard parameter of lbm of fuelbeing burned divided by lbf of thrust the engine produces at thatminimum point. “Low fan pressure ratio” is the pressure ratio across thefan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The lowfan pressure ratio as disclosed herein according to one non-limitingembodiment is less than about 1.55. In another non-limiting embodimentthe low fan pressure ratio is less than about 1.45. In anothernon-limiting embodiment the low fan pressure ratio is from 1.1 to 1.45.“Low corrected fan tip speed” is the actual fan tip speed in ft/secdivided by an industry standard temperature correction of [(Tram °R)/(518.7° R)]^(0.5). The “Low corrected fan tip speed” as disclosedherein according to one non-limiting embodiment is less than about 1150ft/second (350.5 meters/second).

Each of the compressor section 24 and the turbine section 28 may includealternating rows of rotor assemblies and vane assemblies with each ofthe vane assemblies carrying one or more airfoils. The one or moreairfoils extend into the core flow path C. By way of example, the rotorassemblies can carry a plurality of rotating blades 25, while each vaneassembly can carry a plurality of vanes 27 that extend into the coreflow path C. The blades 25 of the rotor assemblies extract energy (inthe form of pressure) from core airflow passing through the gas turbineengine 20. The vanes 27 of the vane assemblies direct core airflow tothe blades 25 of the rotor assemblies to adjust the amount of energyextracted by the blades 25.

Various components of the gas turbine engine 20, including airfoils ofthe compressor section 24 and the turbine section 28, may be subjectedto widely ranging temperatures and pressures and may undergo repetitivethermal cycling. The turbine section 28 is particularly subjected torelatively extreme operating conditions. To compensate for the extremeconditions, some components may require airfoil cooling arrangements forcooling the airfoils that extend into the core flow path C. Exemplaryairfoil cooling arrangements that include internal cooling circuits andfilm cooling holes are described herein.

FIGS. 2 and 3 illustrate a doublet stator vane 50 for utilization in thegas turbine engine 20 of FIG. 1. In alternative examples, the doubletstator vane 50 can be utilized in similar engines. The doublet statorvane 50 includes a pair of airfoils joined to the same inner and outerplatforms. The vane 50 of the exemplary embodiment of FIGS. 2 and 3 is afirst stage turbine vane of the turbine section 28. This disclosure isnot limited to the exemplary embodiment of FIGS. 2 and 3, and couldextend to any vane that is disposed within the core flow path C of thegas turbine engine 20.

The vane 50 includes two airfoils 52, each extending from an innerplatform 54 (on an inner diameter side) to an outer platform 56 (on anouter diameter side). Each airfoil 52 includes a leading edge 58, atrailing edge 60, a pressure side 62 and a suction side 64. Each airfoil52, including the pressure side 62 and the suction side 64, extendsalong a chord Cx from the leading edge 58 and the trailing edge 60 andextends in span S between the inner platform 54 to the outer platform56.

A fluid in the gas path 70 is passed axially downstream through the gasturbine engine 20, along the core flow path C, in a direction thatextends from the leading edge 58 toward the trailing edge 60 of theairfoil 52. The gas path 70 (for the communication of core airfoil alongthe core flow path C) extends between an inner gas path 72 associatedwith the inner platform 54 and an outer gas path 74 associated with theouter platform 56 of the vane 50. The inner platform 54 and the outerplatform 56 are connected to the airfoils 52 at the inner and outer gaspaths 72, 74 via fillets 75.

Both the inner platform 54 and the outer platform 56 include leadingedge rails 66 and trailing edge rails 68. Each of the leading edge rails66 and the trailing edge rails 68 have one or more engagement features69 for mounting the vane 50 to the gas turbine engine 20. By way ofexample, in some cases the leading edge rails 66 and the trailing edgerails 68 are attached to an engine casing. In alternative examples otherengagement features and/or configurations are contemplated as within thescope of this disclosure. Alternative engagement features include butare not limited to, hooks, rails, bolts, rivets, tabs and/or any otherfeatures that can be incorporated into the vane 50 to retain the vane 50to the gas turbine engine 20. In the exemplary embodiment of FIGS. 2 and3, the leading edge rail 66 of the inner platform 54 includes a pin hole82 having a center point 84 (See FIG. 2).

Referring to FIG. 4, the airfoils 52 include an airfoil coolingarrangement having an internal cooling circuit 76 and multiple filmcooling holes 78 that extend through an exterior surface 53 of theairfoil 52. The internal cooling circuit 76 receives a cooling airflowCA to cool the internal surfaces of the airfoil 50 (See FIG. 3). In oneexample, the cooling airflow CA is a bleed airflow that can be sourcedfrom the compressor section 24. In alternative examples the coolingairflow CA can be sourced from any other portion of the gas turbineengine 20 that is upstream from the vane 50. The internal coolingcircuit 76 may include one or more cavities 80 that define hollowopenings within each airfoil 52. The cooling airflow CA is communicatedthrough the cavities 80, which extend across an entire length of theairfoil 52, to cool the internal surfaces of the airfoil 52.

The film cooling holes 78 of the airfoil cooling arrangement are formedthrough the airfoil 52 (between the exterior surface 53 and one or moreof the cavities 80) such that each film cooling hole 78 breaks outthrough the exterior surface 53 of the airfoil 52. In the exemplaryembodiment, each of the leading edge 58, the pressure side 62 and thesuction side 64 includes a plurality of film cooling holes 78. The filmcooling holes 78 may embody a cone shape or a round shape. Other shapesare also contemplated as within the scope of this disclosure.

FIG. 4 illustrates a cross-sectional view of an exemplary airfoil 50.The internal cooling circuit 76 of the airfoil 50 includes multiplecavities 80A-80C that receive cooling airflow CA to cool the internalsurfaces of the airfoil 50. Each of the plurality of film cooling holes78 are in fluid communication with one or more of the cavities 80A-80C.Cooling airflow CA are communicated into and through the cavities80A-80C and are then discharged through the plurality of film coolingholes 78 to provide a boundary layer of film cooling air along theexterior surface 53 of the airfoil 50. The film cooling air provides abarrier that protects the underlying substrate of the airfoil 50 fromthe hot combustion gases that are communicated within the core flow pathC.

The plurality of film cooling holes 78 are spaced apart along the span Sof the airfoil 52 for discharging the cooling airflow CA and providing aboundary layer of film cooling air along the exterior surface 53 of theairfoil 52. In the example embodiment, with reference to FIG. 4 andTable 1, the pressure side 62 includes PA, PB, PC, PD PE, etc. of filmcooling holes 78, the suction side 64 includes SA, SB, SC, etc. of filmcooling holes 78, and the leading edge 58 includes HA, HB, HC, HD, HE,HF, etc. of film cooling holes 78. Additional holes are included in apractical implementation but are not shown for clarity, as evident fromreference to Table 1. Holes identified with the letter “P” refer to therows of the pressure side 62, holes identified with the letter “S” referto the rows of the suction side 64, and holes identified with the letter“H” refer to the rows of the leading edge 58. The locations illustratedin FIG. 4 are schematic in nature, and not drawn to scale.

FIGS. 5A and 5B schematically illustrate the outer and inner platforms56, 54, respectively. The outer and inner platforms 56, 54 include filmcooling holes 90, 92. Holes identified with an “R” relate to the innerplatform holes, such that the inner platform 54 includes film coolingholes 92 RA, RB, RC, RD, etc. Holes identified with an “T” relate to theouter platform holes, such that the outer platform 56 includes filmcooling holes 90 TA, TB, TC, TD, etc. The locations illustrated in FIGS.5A and 5B are schematic in nature, and not drawn to scale.

The breakout position of each of the film cooling holes 78, 90, 92refers to the geometric location along the vane 50 at which the filmcooling hole centerline breaks through or protrudes out of, the exteriorsurface of the vane. The breakout points of each of the plurality offilm cooling holes can be described in terms of sets of Cartesiancoordinates, provided in Table 1 (airfoils) and Table 2 (platforms),defined along x, y and z axes as measured from a specific referencepoint of the vane 50, as is further discussed below. As shown in FIGS. 2and 3 (with continued reference to FIG. 1), the x axis is defined alongthe direction of the engine centerline longitudinal axis A, the y axisis defined in a substantially circumferential or rotational directionabout the engine centerline longitudinal axis A, and the z axis isdefined in a radial direction that is substantially perpendicular to theengine centerline longitudinal axis A.

In these exemplary embodiments, each of the geometric coordinates aremeasured from a pin hole 82 of the leading edge rail 66 of the innerplatform 54 of the vane 50. By measuring the geometric coordinates (interms of x, y and z values) from a center point 84 of the pin hole 82,the external break through points of each film cooling holes 78, 90, 92of the airfoil 52 and inner and outer platforms 54, 56 can beascertained. The Table 1 and Table 2 values for the x, y and zcoordinates represent the true position of a nominal part and are listedin inches in this embodiment. However, the values of the Tables could beconverted to millimeters by multiplying by 25.4, or could be convertedto any other units. The manufacturing tolerance involved in the locationof each film cooling hole 78, 90, 92 is a diameter of approximatelybetween 0 and 0.20 inches (5.08 mm) measured from the surface of thepart. In other words, due to manufacturing tolerances, the externalbreakout of the centerline of each film cooling hole 78 can fall withina 0.20 inch diameter circle inscribed on the surface of the airfoil 50.The variance resultant from the manufacturing tolerance is representedby the ranges of values included in Tables 1 and 2.

Table 1 and Table 2 identify each film cooling hole 78, 90, 92 byassigning a unique, three-letter identifier to each film cooling hole78. The first two letters of the three-letter identifier identify therow (HA, PA, SA, RA, TA) where the film cooling hole is located. Thethird letter corresponds to the specific hole number of a particular rowidentified by the first two letters. The film cooling holes of each roware numbered from the inner platform 54 in a direction toward the outerplatform 56, with the letter A representing the film cooling hole 78closest to the inner platform 54 and subsequent letters assigned to thefilm cooling holes 78 in a direction toward the outer platform 56 (i.e.,B, C, D, etc).

Slab 1-airfoil cooling holes Position Relative to pin hole centerlineHole name x y z RAF HOLES HAA.0001 0.54-0.14 1.3-0.9 1.43-1.03 HAB.00020.6-0.2 1.3-0.9 1.55-1.15 HAC.0003 0.62-0.22 1.31-0.91 1.7-1.3 HAD.00040.62-0.22 1.33-0.93 1.85-1.45 HAE.0005 0.62-0.22 1.34-0.94 1.99-1.59HAF.0006 0.62-0.22 1.35-0.95 2.05-1.65 HAG.0007 0.62-0.22 1.36-0.962.13-1.73 HAH.0008 0.63-0.23 1.38-0.98 2.28-1.88 HAJ.0009 0.63-0.231.39-0.99 2.44-2.04 HAK.0010 0.63-0.23 1.41-1.01 2.59-2.19 HAL.00110.61-0.21 1.44-1.04 2.7-2.3 HBA.0012 0.53-0.13 1.21-0.81 1.44-1.04HBB.0013 0.59-0.19 1.22-0.82 1.6-1.2 HBC.0014 0.59-0.19 1.24-0.841.78-1.38 HBD.0015 0.59-0.19 1.25-0.85 1.92-1.52 HBE.0016 0.59-0.191.27-0.87 2.06-1.66 HBF.0017 0.59-0.19 1.28-0.88 2.12-1.72 HBG.00180.59-0.19 1.29-0.89 2.21-1.81 HBH.0019 0.6-0.2 1.3-0.9 2.34-1.94HBJ.0020 0.6-0.2 1.32-0.92 2.49-2.09 HBK.0021 0.59-0.19 1.35-0.952.66-2.26 HBL.0022 0.49-0.09 1.4-1  2.86-2.46 HCA.0023 0.54-0.141.12-0.72 1.42-1.02 HCB.0024 0.6-0.2 1.14-0.74 1.58-1.18 HCC.00250.6-0.2 1.15-0.75 1.72-1.32 HCD.0026 0.6-0.2 1.16-0.76 1.86-1.46HCE.0027 0.59-0.19 1.18-0.78  2-1.6 HCF.0028 0.59-0.19 1.19-0.792.14-1.74 HCG.0029 0.59-0.19 1.2-0.8 2.19-1.79 HCH.0030 0.59-0.191.21-0.81 2.28-1.88 HCJ.0031 0.6-0.2 1.23-0.83 2.41-2.01 HCK.00320.6-0.2 1.25-0.85 2.55-2.15 HCL.0033 0.59-0.19 1.26-0.86 2.67-2.27HCM.0034 0.56-0.16 1.26-0.86 2.77-2.37 HCN.0035 0.5-0.1 1.25-0.852.86-2.46 HDA.0036 0.57-0.17 1.03-0.63 1.42-1.02 HDB.0037 0.62-0.221.06-0.66 1.61-1.21 HDC.0038 0.62-0.22 1.07-0.67 1.77-1.37 HDD.00390.62-0.22 1.09-0.69 1.91-1.51 HDE.0040 0.62-0.22 1.1-0.7 2.06-1.66HDF.0041 0.62-0.22 1.12-0.72 2.21-1.81 HDG.0042 0.62-0.22 1.13-0.732.26-1.86 HDH.0043 0.62-0.22 1.15-0.75 2.42-2.02 HDJ.0044 0.62-0.221.17-0.77 2.57-2.17 HDK.0045 0.61-0.21 1.18-0.78 2.7-2.3 HDL.00460.58-0.18 1.18-0.78 2.8-2.4 HDM.0047 0.5-0.1 1.16-0.76 2.9-2.5 HEA.00480.65-0.25 1.11-0.71 2.75-2.35 HEB.0049 0.61-0.21 1.11-0.71 2.83-2.43HFA.0050 0.67-0.27 1.07-0.67 2.83-2.43 HFB.0051 0.61-0.21 1.06-0.662.89-2.49 HFC.0052 0.72-0.32 1.03-0.63 2.88-2.48 HFD.0053 0.79-0.391.03-0.63 2.86-2.46 PAA.0054 1.44-1.04 2.44-2.04 1.46-1.06 PAA.00551.44-1.04 2.49-2.09 1.6-1.2 PAA.0056 1.44-1.04 2.53-2.13 1.73-1.33PAA.0057 1.44-1.04 2.56-2.16 1.87-1.47 PAA.0058 1.44-1.04 2.59-2.192.02-1.62 PAA.0059 1.44-1.04 2.61-2.21 2.16-1.76 PAA.0060 1.44-1.042.62-2.22 2.31-1.91 PAA.0061 1.44-1.04 2.63-2.23 2.45-2.05 PAB.00621.45-1.05 2.72-2.32 2.56-2.16 PBA.0063 1.41-1.01 2.4-2  1.52-1.12PBA.0064 1.41-1.01 2.45-2.05 1.66-1.26 PBA.0065 1.41-1.01 2.49-2.091.8-1.4 PBA.0066 1.42-1.02 2.52-2.12 1.94-1.54 PBA.0067 1.42-1.022.55-2.15 2.08-1.68 PBA.0068 1.42-1.02 2.57-2.17 2.23-1.83 PBA.00691.42-1.02 2.58-2.18 2.37-1.97 PCA.0070 1.36-0.96 2.27-1.87 1.47-1.07PCA.0071 1.36-0.96 2.32-1.92 1.6-1.2 PCA.0072 1.36-0.96 2.36-1.961.74-1.34 PCA.0073 1.36-0.96 2.39-1.99 1.88-1.48 PCA.0074 1.36-0.962.42-2.02 2.02-1.62 PCA.0075 1.36-0.96 2.44-2.04 2.17-1.77 PCA.00761.36-0.96 2.46-2.06 2.31-1.91 PCA.0077 1.36-0.96 2.47-2.07 2.46-2.06PDA.0078 1.26-0.86 2.13-1.73 1.54-1.14 PDA.0079 1.26-0.86 2.16-1.761.68-1.28 PDA.0080 1.26-0.86 2.2-1.8 1.82-1.42 PDA.0081 1.26-0.862.23-1.83 1.96-1.56 PDA.0082 1.26-0.86 2.25-1.85 2.1-1.7 PDA.00831.26-0.86 2.27-1.87 2.24-1.84 PDA.0084 1.26-0.86 2.29-1.89 2.38-1.98PDA.0085 1.26-0.86 2.31-1.91 2.52-2.12 PDB.0086 1.29-0.89 2.38-1.982.6-2.2 PDC.0087 1.23-0.83 2.36-1.96 2.7-2.3 PEA.0088 1.16-0.761.96-1.56 1.53-1.13 PEA.0089 1.16-0.76 1.98-1.58 1.67-1.27 PEA.00901.15-0.75  2-1.6 1.82-1.42 PEA.0091 1.14-0.74 2.02-1.62 1.96-1.56PEA.0092 1.14-0.74 2.03-1.63 2.1-1.7 PEA.0093 1.13-0.73 2.05-1.652.25-1.85 PEA.0094 1.12-0.72 2.06-1.66 2.39-1.99 PEA.0095 1.12-0.722.07-1.67 2.53-2.13 PEB.0096 1.12-0.72 2.12-1.72 2.67-2.27 PEC.00971.08-0.68 2.1-1.7 2.73-2.33 PFA.0098 0.94-0.54 1.67-1.27 1.49-1.09PFB.0099 0.95-0.55 1.69-1.29 1.66-1.26 PFB.0100 0.95-0.55 1.71-1.311.82-1.42 PFB.0101 0.95-0.55 1.73-1.33 1.98-1.58 PFB.0102 0.96-0.561.75-1.35 2.14-1.74 PFB.0103 0.96-0.56 1.78-1.38 2.3-1.9 PFB.01040.97-0.57 1.82-1.42 2.46-2.06 PGA.0105 0.81-0.41 1.58-1.18 1.42-1.02PGB.0106 0.83-0.43 1.54-1.14 1.59-1.19 PGC.0107 0.83-0.43 1.55-1.151.76-1.36 PGC.0108 0.83-0.43 1.56-1.16 1.92-1.52 PGC.0109 0.83-0.431.58-1.18 2.08-1.68 PGC.0110 0.84-0.44 1.6-1.2 2.24-1.84 PGC.01110.84-0.44 1.63-1.23 2.4-2  PGC.0112 0.84-0.44 1.66-1.26 2.56-2.16PHA.0113 0.69-0.29 1.41-1.01 1.54-1.14 PHA.0114 0.69-0.29 1.41-1.011.61-1.21 PHA.0115 0.7-0.3 1.41-1.01 1.69-1.29 PHA.0116 0.7-0.31.41-1.01 1.77-1.37 PHA.0117 0.7-0.3 1.42-1.02 1.86-1.46 PHA.01180.7-0.3 1.42-1.02 1.95-1.55 PHA.0119 0.7-0.3 1.43-1.03 2.03-1.63PHB.0120 0.69-0.29 1.44-1.04 2.16-1.76 PHB.0121 0.7-0.3 1.45-1.052.25-1.85 PHB.0122 0.7-0.3 1.46-1.06 2.34-1.94 PHB.0123 0.7-0.31.47-1.07 2.43-2.03 PHB.0124 0.7-0.3 1.48-1.08 2.51-2.11 PHB.01250.7-0.3 1.5-1.1 2.6-2.2 PHC.0126 0.71-0.31 1.52-1.12 2.66-2.26 PHD.01270.71-0.31 1.55-1.15 2.72-2.32 RMA.0128 1.35-0.95 2.32-1.92 1.26-0.86RMB.0129 1.27-0.87 2.25-1.85 1.23-0.83 RMC.0130 1.3-0.9 2.21-1.811.29-0.89 RMD.0131 0.59-0.19 1.51-1.11 1.31-0.91 RME.0132 0.49-0.091.38-0.98 1.32-0.92 RMF.0133 0.41-0.01 1.22-0.82 1.29-0.89 RMG.0134 0.36-−0.04 1.1-0.7 1.25-0.85 RMH.0135 0.47-0.07 0.93-0.53 1.29-0.89RMJ.0136 0.41-0.01 0.89-0.49 1.26-0.86 RMK.0137 0.47-0.07 0.83-0.431.27-0.87 RML.0138 0.6-0.2 0.77-0.37 1.33-0.93 RMM.0139 1.17-0.771.09-0.69 1.42-1.02 RNA.0140 1.5-1.1 2.05-1.65 1.3-0.9 RNB.01411.49-1.09 2.1-1.7 1.32-0.92 SAA.0142 0.75-0.35 0.9-0.5 1.5-1.1 SAA.01430.75-0.35 0.92-0.52 1.57-1.17 SAA.0144 0.75-0.35 0.93-0.53 1.64-1.24SAA.0145 0.75-0.35 0.94-0.54 1.71-1.31 SAA.0146 0.75-0.35 0.95-0.551.79-1.39 SAA.0147 0.75-0.35 0.95-0.55 1.86-1.46 SAA.0148 0.75-0.350.96-0.56 1.94-1.54 SAA.0149 0.75-0.35 0.97-0.57 2.01-1.61 SAA.01500.75-0.35 0.98-0.58 2.09-1.69 SAA.0151 0.75-0.35 0.99-0.59 2.16-1.76SAB.0152 0.75-0.35  1-0.6 2.25-1.85 SAB.0153 0.75-0.35  1-0.6 2.33-1.93SAB.0154 0.74-0.34 1.01-0.61 2.4-2  SAB.0155 0.74-0.34 1.02-0.622.48-2.08 SAB.0156 0.74-0.34 1.03-0.63 2.56-2.16 SAB.0157 0.74-0.341.04-0.64 2.63-2.23 SAB.0158 0.74-0.34 1.05-0.65 2.71-2.31 SAB.01590.74-0.34 1.05-0.65 2.78-2.38 SBA.0160 0.98-0.58 0.96-0.56 1.51-1.11SBA.0161 0.98-0.58 0.97-0.57 1.58-1.18 SBA.0162 0.98-0.58 0.98-0.581.66-1.26 SBA.0163 0.98-0.58 0.99-0.59 1.74-1.34 SBA.0164 0.99-0.59 1-0.6 1.82-1.42 SBA.0165 0.99-0.59  1-0.6 1.89-1.49 SBA.0166 0.99-0.591.01-0.61 1.97-1.57 SBA.0167 0.99-0.59 1.02-0.62 2.05-1.65 SBA.0168 1-0.6 1.03-0.63 2.13-1.73 SBA.0169  1-0.6 1.04-0.64 2.2-1.8 SBA.0170 1-0.6 1.05-0.65 2.28-1.88 SBA.0171  1-0.6 1.05-0.65 2.36-1.96 SBA.0172 1-0.6 1.06-0.66 2.44-2.04 SBA.0173  1-0.6 1.07-0.67 2.51-2.11 SBA.0174 1-0.6 1.08-0.68 2.59-2.19 SBA.0175  1-0.6 1.09-0.69 2.67-2.27 SBA.0176 1-0.6 1.1-0.7 2.75-2.35 SBA.0177  1-0.6 1.11-0.71 2.82-2.42 SBB.01780.98-0.58 1.08-0.68 2.87-2.47 SCA.0179 1.14-0.74 1.14-0.74 1.53-1.13SCA.0180 1.14-0.74 1.14-0.74 1.6-1.2 SCA.0181 1.14-0.74 1.15-0.751.68-1.28 SCA.0182 1.14-0.74 1.16-0.76 1.76-1.36 SCA.0183 1.14-0.741.16-0.76 1.84-1.44 SCA.0184 1.14-0.74 1.17-0.77 1.92-1.52 SCA.01851.14-0.74 1.18-0.78 1.99-1.59 SCA.0186 1.14-0.74 1.18-0.78 2.07-1.67SCA.0187 1.14-0.74 1.19-0.79 2.15-1.75 SCA.0188 1.13-0.73 1.2-0.82.23-1.83 SCA.0189 1.13-0.73 1.2-0.8 2.3-1.9 SCA.0190 1.13-0.731.21-0.81 2.38-1.98 SCA.0191 1.13-0.73 1.22-0.82 2.46-2.06 SCA.01921.13-0.73 1.23-0.83 2.54-2.14 SCA.0193 1.13-0.73 1.23-0.83 2.61-2.21SCA.0194 1.13-0.73 1.24-0.84 2.69-2.29 SCB.0195 1.08-0.68 1.18-0.782.75-2.35 SCC.0196 1.08-0.68 1.19-0.79 2.81-2.41 SDA.0197 1.52-1.122.37-1.97 2.61-2.21 SDB.0198 1.58-1.18 2.57-2.17 2.59-2.19 SDC.01991.56-1.16 2.44-2.04 2.65-2.25 TCH.0200 1.62-1.22 2.57-2.17 2.65-2.25TCJ.0201 1.64-1.24 2.74-2.34 2.61-2.21 TDA.0202 1.45-1.05 2.82-2.422.62-2.22 TPA.0203 0.61-0.21 1.74-1.34 2.89-2.49 TPB.0204 0.49-0.091.77-1.37 2.92-2.52 TPC.0205 0.65-0.25 1.62-1.22 2.83-2.43 TPD.02060.54-0.14 1.64-1.24 2.89-2.49 TPE.0207 0.56-0.16 1.52-1.12 2.82-2.42TPF.0208 0.48-0.08 1.46-1.06 2.88-2.48 TPG.0209 0.41-0.01 1.52-1.122.94-2.54 TPH.0210 0.4-0  1.31-0.91 2.94-2.54 TPJ.0211 0.42-0.021.17-0.77 2.96-2.56 TPK.0212 0.42-0.02 1.08-0.68 2.98-2.58 TPL.02130.42-0.02 0.99-0.59 2.99-2.59 TPM.0214 0.56-0.16 0.95-0.55 2.99-2.59TRA.0215 1.31-0.91 1.41-1.01 2.88-2.48 TRB.0216 1.26-0.86 1.43-1.032.84-2.44 LAF HOLES HGA.0001 0.55-0.15 −0.3-−0.7 1.39-0.99 HGB.00020.6-0.2 −0.31-−0.71 1.5-1.1 HGC.0003 0.62-0.22 −0.33-−0.73 1.66-1.26HGD.0004 0.62-0.22 −0.35-−0.75 1.8-1.4 HGE.0005 0.62-0.22 −0.36-−0.761.95-1.55 HGF.0006 0.62-0.22 −0.36-−0.76  2-1.6 HGG.0007 0.62-0.22−0.37-−0.77 2.09-1.69 HGH.0008 0.63-0.23 −0.38-−0.78 2.24-1.84 HGJ.00090.63-0.23 −0.4-−0.8 2.4-2  HGK.0010 0.63-0.23 −0.41-−0.81 2.56-2.16HGL.0011 0.61-0.21 −0.4-−0.8 2.67-2.27 HHA.0012 0.54-0.14 −0.38-−0.781.38-0.98 HHB.0013 0.59-0.19 −0.4-−0.8 1.54-1.14 HHC.0014 0.59-0.19−0.42-−0.82 1.72-1.32 HHD.0015 0.59-0.19 −0.43-−0.83 1.86-1.46 HHE.00160.59-0.19 −0.45-−0.85 2.01-1.61 HHF.0017 0.59-0.19 −0.45-−0.85 2.06-1.66HHG.0018 0.59-0.19 −0.45-−0.85 2.15-1.75 HHH.0019 0.6-0.2 −0.46-−0.862.29-1.89 HHJ.0020 0.6-0.2 −0.47-−0.87 2.43-2.03 HHK.0021 0.59-0.19−0.48-−0.88 2.61-2.21 HHL.0022 0.49-0.09 −0.48-−0.88 2.81-2.41 HJA.00230.54-0.14 −0.47-−0.87 1.35-0.95 HJB.0024 0.6-0.2 −0.48-−0.88 1.51-1.11HJC.0025 0.6-0.2 −0.5-−0.9 1.65-1.25 HJD.0026 0.6-0.2 −0.51-−0.911.79-1.39 HJE.0027 0.59-0.19 −0.52-−0.92 1.93-1.53 HJF.0028 0.59-0.19−0.53-−0.93 2.07-1.67 HJG.0029 0.59-0.19 −0.54-−0.94 2.12-1.72 HJH.00300.59-0.19 −0.54-−0.94 2.21-1.81 HJJ.0031 0.6-0.2 −0.55-−0.95 2.34-1.94HJK.0032 0.6-0.2 −0.56-−0.96 2.48-2.08 HJL.0033 0.59-0.19 −0.57-−0.972.6-2.2 HJM.0034 0.56-0.16 −0.59-−0.99 2.7-2.3 HJN.0035 0.51-0.11−0.62-−1.02 2.79-2.39 HKA.0036 0.57-0.17 −0.56-−0.96 1.33-0.93 HKB.00370.62-0.22 −0.57-−0.97 1.52-1.12 HKC.0038 0.62-0.22 −0.58-−0.98 1.68-1.28HKD.0039 0.62-0.22 −0.59-−0.99 1.82-1.42 HKE.0040 0.62-0.22 −0.61-−1.011.97-1.57 HKF.0041 0.62-0.22 −0.62-−1.02 2.12-1.72 HKG.0042 0.62-0.22−0.62-−1.02 2.18-1.78 HKH.0043 0.62-0.22 −0.63-−1.03 2.33-1.93 HKJ.00440.62-0.22 −0.64-−1.04 2.48-2.08 HKK.0045 0.61-0.21 −0.66-−1.06 2.62-2.22HKL.0046 0.58-0.18 −0.67-−1.07 2.72-2.32 HKM.0047 0.5-0.1 −0.72-−1.122.81-2.41 PKA.0048 1.44-1.04 0.82-0.42 1.64-1.24 PKA.0049 1.44-1.040.84-0.44 1.78-1.38 PKA.0050 1.44-1.04 0.85-0.45 1.93-1.53 PKA.00511.44-1.04 0.86-0.46 2.07-1.67 PKA.0052 1.44-1.04 0.86-0.46 2.22-1.82PKA.0053 1.44-1.04 0.85-0.45 2.36-1.96 PKA.0054 1.44-1.04 0.84-0.442.51-2.11 PKA.0055 1.44-1.04 0.81-0.41 2.66-2.26 PKB.0056 1.42-1.020.81-0.41 2.78-2.38 PLA.0057 1.41-1.01 0.77-0.37 1.7-1.3 PLA.00581.41-1.01 0.79-0.39 1.84-1.44 PLA.0059 1.41-1.01 0.8-0.4 1.98-1.58PLA.0060 1.42-1.02 0.8-0.4 2.13-1.73 PLA.0061 1.42-1.02 0.8-0.42.27-1.87 PLA.0062 1.42-1.02 0.8-0.4 2.42-2.02 PLA.0063 1.42-1.020.78-0.38 2.56-2.16 PMA.0064 1.36-0.96 0.65-0.25 1.61-1.21 PMA.00651.36-0.96 0.67-0.27 1.76-1.36 PMA.0066 1.36-0.96 0.69-0.29 1.9-1.5PMA.0067 1.36-0.96 0.69-0.29 2.05-1.65 PMA.0068 1.36-0.96 0.69-0.292.19-1.79 PMA.0069 1.36-0.96 0.69-0.29 2.34-1.94 PMA.0070 1.36-0.960.68-0.28 2.48-2.08 PMA.0071 1.36-0.96 0.66-0.26 2.63-2.23 PNA.00721.26-0.86 0.5-0.1 1.66-1.26 PNA.0073 1.26-0.86 0.51-0.11 1.81-1.41PNA.0074 1.26-0.86 0.51-0.11 1.95-1.55 PNA.0075 1.26-0.86 0.51-0.112.09-1.69 PNA.0076 1.26-0.86 0.51-0.11 2.24-1.84 PNA.0077 1.26-0.860.51-0.11 2.38-1.98 PNA.0078 1.26-0.86 0.5-0.1 2.52-2.12 PNA.00791.26-0.86 0.48-0.08 2.66-2.26 PNB.0080 1.29-0.89 0.54-0.14 2.75-2.35PPA.0081 1.16-0.76  0.34-−0.06 1.62-1.22 PPA.0082 1.16-0.76  0.33-−0.071.76-1.36 PPA.0083 1.15-0.75  0.32-−0.08 1.91-1.51 PPA.0084 1.14-0.74 0.31-−0.09 2.05-1.65 PPA.0085 1.14-0.74  0.3-−0.1 2.19-1.79 PPA.00861.13-0.73  0.28-−0.12 2.34-1.94 PPA.0087 1.12-0.72  0.26-−0.14 2.48-2.08PPA.0088 1.12-0.72  0.25-−0.15 2.62-2.22 PRA.0089 0.94-0.54  0.06-−0.341.53-1.13 PRB.0090 0.95-0.55  0.05-−0.35 1.69-1.29 PRB.0091 0.95-0.55 0.03-−0.37 1.85-1.45 PRB.0092 0.95-0.55  0.02-−0.38 2.01-1.61 PRB.00930.96-0.56  0.02-−0.38 2.17-1.77 PRB.0094 0.96-0.56  0.02-−0.38 2.34-1.94PRB.0095 0.97-0.57  0.02-−0.38 2.5-2.1 PSA.0096 0.81-0.41 −0.01-−0.411.44-1.04 PSB.0097 0.83-0.43 −0.09-−0.49 1.6-1.2 PSC.0098 0.83-0.43−0.11-−0.51 1.76-1.36 PSC.0099 0.83-0.43 −0.13-−0.53 1.93-1.53 PSC.01000.83-0.43 −0.15-−0.55 2.09-1.69 PSC.0101 0.84-0.44 −0.16-−0.56 2.25-1.85PSC.0102 0.84-0.44 −0.16-−0.56 2.41-2.01 PSC.0103 0.84-0.44 −0.16-−0.562.57-2.17 PTA.0104 0.69-0.29 −0.2-−0.6 1.52-1.12 PTA.0105 0.69-0.29−0.22-−0.62 1.59-1.19 PTA.0106 0.7-0.3 −0.24-−0.64 1.67-1.27 PTA.01070.7-0.3 −0.25-−0.65 1.75-1.35 PTA.0108 0.7-0.3 −0.26-−0.66 1.83-1.43PTA.0109 0.7-0.3 −0.27-−0.67 1.92-1.52 PTA.0110 0.7-0.3 −0.28-−0.682.01-1.61 PTB.0111 0.69-0.29 −0.3-−0.7 2.13-1.73 PTB.0112 0.7-0.3−0.31-−0.71 2.22-1.82 PTB.0113 0.7-0.3 −0.31-−0.71 2.31-1.91 PTB.01140.7-0.3 −0.32-−0.72 2.4-2  PTB.0115 0.7-0.3 −0.32-−0.72 2.49-2.09PTB.0116 0.7-0.3 −0.33-−0.73 2.58-2.18 RLA.0117 1.44-1.04 0.97-0.571.41-1.01 RLB.0118 1.33-0.93 0.71-0.31 1.41-1.01 RLC.0119 0.61-0.21 0.04-−0.36 1.3-0.9 RLD.0120 0.51-0.11 −0.06-−0.46 1.28-0.88 RLE.01210.41-0.01 −0.16-−0.56 1.24-0.84 RLF.0122 0.42-0.02 −0.28-−0.68 1.25-0.85RLG.0123 0.45-0.05 −0.44-−0.84 1.25-0.85 RLH.0124 0.42-0.02 −0.54-−0.941.18-0.78 RLJ.0125 0.5-0.1 −0.69-−1.09 1.17-0.77 RLK.0126 0.59-0.19−0.68-−1.08 1.23-0.83 RLL.0127 1.56-1.16 0.67-0.27 1.44-1.04 RLM.01281.6-1.2 0.76-0.36 1.42-1.02 SFA.0129 0.75-0.35 −0.7-−1.1 1.38-0.98SFA.0130 0.75-0.35 −0.69-−1.09 1.45-1.05 SFA.0131 0.75-0.35 −0.7-−1.11.52-1.12 SFA.0132 0.75-0.35 −0.7-−1.1 1.6-1.2 SFA.0133 0.75-0.35−0.71-−1.11 1.67-1.27 SFA.0134 0.75-0.35 −0.71-−1.11 1.75-1.35 SFA.01350.75-0.35 −0.72-−1.12 1.82-1.42 SFA.0136 0.75-0.35 −0.73-−1.13 1.9-1.5SFA.0137 0.75-0.35 −0.73-−1.13 1.97-1.57 SFA.0138 0.75-0.35 −0.74-−1.142.05-1.65 SFB.0139 0.75-0.35 −0.75-−1.15 2.14-1.74 SFB.0140 0.75-0.35−0.76-−1.16 2.21-1.81 SFB.0141 0.74-0.34 −0.76-−1.16 2.29-1.89 SFB.01420.74-0.34 −0.77-−1.17 2.37-1.97 SFB.0143 0.74-0.34 −0.78-−1.18 2.44-2.04SFB.0144 0.74-0.34 −0.78-−1.18 2.52-2.12 SFB.0145 0.74-0.34 −0.79-−1.192.6-2.2 SFB.0146 0.74-0.34 −0.8-−1.2 2.67-2.27 SGA.0147 1.14-0.74−0.47-−0.87 1.45-1.05 SGA.0148 1.14-0.74 −0.48-−0.88 1.53-1.13 SGA.01491.14-0.74 −0.49-−0.89 1.61-1.21 SGA.0150 1.14-0.74 −0.5-−0.9 1.69-1.29SGA.0151 1.14-0.74 −0.51-−0.91 1.76-1.36 SGA.0152 1.14-0.74 −0.51-−0.911.84-1.44 SGA.0153 1.14-0.74 −0.52-−0.92 1.92-1.52 SGA.0154 1.14-0.74−0.53-−0.93  2-1.6 SGA.0155 1.14-0.74 −0.54-−0.94 2.07-1.67 SGA.01561.13-0.73 −0.55-−0.95 2.15-1.75 SGA.0157 1.13-0.73 −0.56-−0.96 2.23-1.83SGA.0158 1.13-0.73 −0.56-−0.96 2.31-1.91 SGA.0159 1.13-0.73 −0.57-−0.972.38-1.98 SGA.0160 1.13-0.73 −0.58-−0.98 2.46-2.06 SGA.0161 1.13-0.73−0.59-−0.99 2.54-2.14 SGA.0162 1.13-0.73 −0.6-−1  2.62-2.22 SGB.01631.08-0.68 −0.67-−1.07 2.66-2.26 SGC.0164 1.08-0.68 −0.67-−1.07 2.73-2.33TNA.0165 1.34-0.94 0.81-0.41 2.88-2.48 TNB.0166 1.31-0.91 0.71-0.312.88-2.48 TNC.0167 0.83-0.43  0.18-−0.22 2.96-2.56 TND.0168 0.54-0.14−0.18-−0.58 2.92-2.52 TNE.0169 0.45-0.05 −0.3-−0.7 2.91-2.51 TNF.01700.45-0.05 −0.42-−0.82 2.87-2.47 TNG.0171 0.4-0  −0.51-−0.91 2.89-2.49TNH.0172 0.46-0.06 −0.66-−1.06 2.83-2.43 TNJ.0173 0.4-0  −0.72-−1.122.87-2.47 TNK.0174 0.45-0.05 −0.81-−1.21 2.86-2.46 TNL.0175 0.48-0.08−0.91-−1.31 2.85-2.45 TNM.0176 0.58-0.18 −0.88-−1.28 2.83-2.43 TNN.01770.74-0.34 −0.93-−1.33 2.85-2.45 TNP.0178 0.87-0.47 −0.88-−1.28 2.81-2.41TNR.0179 1.22-0.82 −0.62-−1.02 2.82-2.42 TNS.0180 1.3-0.9 −0.57-−0.972.84-2.44 TNT.0181 1.48-1.08 −0.05-−0.45 2.86-2.46 TNU.0182 1.64-1.240.77-0.37 2.84-2.44

TABLE 2 platform cooling holes Position Relative to pin hole centerlineHole name x y z OD PLATFORM TAA.0001 1.68-1.28 −0.37-−0.77 2.79-2.39TBA.0002 1.63-1.23 −0.15-−0.55 2.82-2.42 TBB.0003 1.62-1.22 −0.03-−0.432.83-2.43 TBC.0004 1.62-1.22  0.09-−0.31 2.84-2.44 TBD.0005 1.62-1.22 0.21-−0.19 2.85-2.45 TCA.0006 1.62-1.22 1.38-0.98 2.82-2.42 TCB.00071.62-1.22 1.51-1.11 2.82-2.42 TCC.0008 1.62-1.22 1.66-1.26 2.81-2.41TCD.0009 1.62-1.22 1.83-1.43 2.79-2.39 TCE.0010 1.63-1.23 2.03-1.632.77-2.37 TCF.0011 1.63-1.23 2.21-1.81 2.74-2.34 TCG.0012 1.63-1.232.4-2  2.7-2.3 TDB.0013 1.37-0.97 2.69-2.29 2.67-2.27 TDC.0014 1.27-0.872.61-2.21 2.71-2.31 TDD.0015 1.2-0.8 2.52-2.12 2.74-2.34 TEA.00161.25-0.85 0.82-0.42 2.91-2.51 TEB.0017 1.09-0.69 0.95-0.55 2.95-2.55TFB.0018 0.94-0.54 0.77-0.37 2.99-2.59 TFC.0019 0.84-0.44 0.83-0.433.01-2.61 TFD.0020 0.94-0.54 0.92-0.52 2.98-2.58 TGA.0021 1.08-0.680.49-0.09 2.94-2.54 TGB.0022 0.98-0.58 0.53-0.13 2.97-2.57 TGC.00230.88-0.48 0.58-0.18  3-2.6 THA.0024 0.78-0.38  0.26-−0.14 2.98-2.58THB.0025 0.73-0.33  0.33-−0.07 2.99-2.59 THC.0026 0.69-0.29 0.43-0.03 3-2.6 TJA.0027 0.71-0.31 0.62-0.22 3.02-2.62 TJC.0028 0.63-0.230.76-0.36 3.01-2.61 TKA.0029 0.59-0.19 0.87-0.47  3-2.6 TLA.00301.11-0.71 2.42-2.02 2.78-2.38 TLB.0031 1.03-0.63 2.25-1.85 2.82-2.42TLC.0032  1-0.6 2.35-1.95 2.83-2.43 TLD.0033 0.93-0.53 2.15-1.752.86-2.46 TLE.0034 0.89-0.49 2.26-1.86 2.86-2.46 TLF.0035 0.8-0.42.13-1.73 2.88-2.48 TMA.0036 0.64-0.24  0.03-−0.37 2.95-2.55 TSA.00371.56-1.16 −0.6-−1  2.76-2.36 TSB.0038 1.46-1.06 −0.59-−0.99 2.81-2.41TSC.0039 1.27-0.87 −0.77-−1.17 2.82-2.42 TTA.0040 1.46-1.06 −0.49-−0.892.82-2.42 TTB.0041 1.56-1.16 −0.46-−0.86 2.79-2.39 TTC.0042 1.45-1.05−0.39-−0.79 2.84-2.44 TTD.0043 1.52-1.12 −0.28-−0.68 2.84-2.44 TTE.00441.55-1.15 −0.12-−0.52 2.84-2.44 TUA.0045 1.67-1.27 −0.63-−1.03 2.82-2.42TUB.0046 1.59-1.19 −0.69-−1.09 2.8-2.4 TUC.0047 1.5-1.1 −0.75-−1.152.82-2.42 TUD.0048 1.42-1.02 −0.82-−1.22 2.83-2.43 TUE.0049 1.29-0.89−0.91-−1.31 2.85-2.45 TUF.0050 1.24-0.84 −0.95-−1.35 2.85-2.45 TUG.00510.57-0.17 −1.45-−1.85 2.82-2.42 TUH.0052 0.49-0.09 −1.51-−1.91 2.8-2.4TVA.0053 1.63-1.23 3.04-2.64 2.61-2.21 TVB.0054 1.54-1.14 2.98-2.582.62-2.22 TVC.0055 1.45-1.05 2.92-2.52 2.67-2.27 TVD.0056 1.38-0.982.87-2.47 2.7-2.3 TVE.0057 0.54-0.14 2.29-1.89 2.93-2.53 TVF.00580.46-0.06 2.22-1.82 2.93-2.53 TWA.0059 1.76-1.36 −0.28-−0.68 2.88-2.48TWB.0060 1.76-1.36 0.92-0.52 2.92-2.52 TWC.0061 1.76-1.36 1.17-0.772.91-2.51 TWD.0062 1.76-1.36 1.42-1.02 2.9-2.5 TWE.0063 1.76-1.362.85-2.45 2.69-2.29 TYA.0064 1.21-0.81 1.03-0.63 2.93-2.53 TYB.00651.37-0.97 1.08-0.68 2.9-2.5 TYC.0066 1.41-1.01  1-0.6 2.88-2.48 TZA.00670.6-0.2 −0.97-−1.37 2.85-2.45 TZB.0068 0.62-0.22 −1.1-−1.5 2.84-2.44TZC.0069 0.44-0.04  0.04-−0.36 2.96-2.56 TZD.0070 0.44-0.04  0.23-−0.172.98-2.58 TZE.0071 0.44-0.04 0.42-0.02 2.98-2.58 TZF.0072 0.45-0.050.64-0.24 2.99-2.59 TZG.0073 0.44-0.04 0.83-0.43 2.99-2.59 ID PLATFORMRAA.0001 1.59-1.19 −0.23-−0.63 1.35-0.95 RAB.0002 1.53-1.13 −0.26-−0.661.34-0.94 RAC.0003 1.45-1.05 −0.31-−0.71 1.33-0.93 RAD.0004 1.39-0.99−0.33-−0.73 1.32-0.92 RBA.0005 1.55-1.15  0.29-−0.11 1.39-0.99 RBB.00061.52-1.12  0.33-−0.07 1.39-0.99 RBC.0007 1.5-1.1  0.39-−0.01 1.4-1 RBD.0008 1.59-1.19  0.14-−0.26 1.38-0.98 RBE.0009 1.48-1.08  0.1-−0.31.37-0.97 RCA.0010 1.51-1.11 1.14-0.74 1.4-1  RCB.0011 1.52-1.121.31-0.91 1.38-0.98 RDA.0012 1.59-1.19 1.62-1.22 1.35-0.95 RDB.00131.58-1.18 1.79-1.39 1.33-0.93 RDC.0014 1.58-1.18 1.87-1.47 1.32-0.92RDD.0015 1.57-1.17 1.94-1.54 1.3-0.9 REA.0016 1.22-0.82 0.96-0.561.39-0.99 RFA.0017 1.09-0.69 0.51-0.11 1.37-0.97 RFB.0018 1.08-0.680.64-0.24 1.36-0.96 RFC.0019 1.04-0.64 0.8-0.4 1.37-0.97 RGA.00200.89-0.49  0.36-−0.04 1.34-0.94 RGB.0021 0.83-0.43 0.43-0.03 1.31-0.91RGC.0022 0.81-0.41 0.54-0.14 1.32-0.92 RGD.0023 0.82-0.42 0.73-0.331.37-0.97 RHA.0024 0.65-0.25 0.63-0.23 1.33-0.93 RJA.0025 1.01-0.612.03-1.63 1.25-0.85 RJB.0026 0.88-0.48 1.99-1.59 1.22-0.82 RKA.00270.43-0.03 −0.74-−1.14 1.13-0.73 RPA.0028 0.4-0  1.78-1.38 1.11-0.71

Although the different non-limiting embodiments are illustrated ashaving specific components, the embodiments of this disclosure are notlimited to those particular combinations. It is possible to use some ofthe components or features from any of the non-limiting embodiments incombination with features or components from any of the othernon-limiting embodiments.

It should be understood that like reference numerals identifycorresponding or similar elements throughout the several drawings. Itshould also be understood that although a particular componentarrangement is disclosed and illustrated in these exemplary embodiments,other arrangements could also benefit from the teachings of thisdisclosure.

In some examples, such as examples utilizing the above described holeplacement and configurations of tables 1 and 2, the doublet stator vaneis constructed using a casting process, with some or all of the filmcooling holes being defined by a casting die. In alternative examples aportion of the film cooling holes can be created post casting using amachining process such as an electrical discharge machining (EDM)process, or the like.

The foregoing description shall be interpreted as illustrative and notin any limiting sense. A worker of ordinary skill in the art wouldrecognize that various modifications could come within the scope of thisdisclosure. For these reasons, the following claims should be studied todetermine the true scope and content of this disclosure.

What is claimed is:
 1. A vane comprising: a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of said airfoils, wherein each of said plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1, wherein each of said geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
 2. The vane as recited in claim 1, wherein said Cartesian coordinate values of Table 1 are expressed in inches.
 3. The vane as recited in claim 1, wherein said reference point includes a pin hole of said platform.
 4. The vane as recited in claim 1, wherein said plurality of film cooling holes are spaced along a span of said airfoil body in multiple collinearly aligned rows.
 5. The vane as recited in claim 1, wherein said plurality of film cooling holes are disposed on a pressure side, a suction side and a leading edge of said airfoil body.
 6. The vane as recited in claim 1, wherein a first portion of said plurality of film cooling holes from a point of said airfoil body toward an outer platform are angled toward said outer platform and a second portion of said plurality of film cooling holes from said point toward an inner platform are angled inwardly toward said inner platform.
 7. The vane as recited in claim 1, wherein the airfoils extend between inner and outer platforms, the inner and outer platforms include another plurality of film cooling holes that extend through an exterior surface of said platforms, wherein each of said other plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 2, wherein each of said geometric coordinates is measured from the reference point.
 8. A vane comprising: a pair of airfoils extending between inner and outer platforms, the inner and outer platforms include a plurality of film cooling holes that extend through an exterior surface of said platforms, wherein each of said plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 2, wherein each of said geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
 9. The vane as recited in claim 8, wherein said Cartesian coordinate values of Table 2 are expressed in inches.
 10. The vane as recited in claim 8, wherein said reference point includes a pin hole of said platform.
 11. A vane comprising: a pair of airfoils extending between inner and outer platforms, the inner and outer platforms include a plurality of film cooling holes that extend through an exterior surface of said platforms, wherein each of said plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 2, wherein each of said geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
 12. The vane as recited in claim 11, wherein said Cartesian coordinate values of Table 2 are expressed in inches.
 13. The vane as recited in claim 11, wherein said reference point includes a pin hole of said platform. 